Experimental Data and MATLAB Code for Velocity-Dependent Aerodynamic Control Effectiveness Analysis of the Aquila-S Flapping-Wing Vehicle

This repository contains the experimental data and MATLAB code supporting the study “Speed-Dependent Aerodynamic Control Effectiveness of a Flapping-Wing Vehicle.” The experiments were conducted on the Aquila-S flapping-wing vehicle using a six-component force balance under freestream velocities of 3, 5, and 7 m/s. The investigated control inputs include flapping frequency, pitch-tail deflection, and roll-tail deflection. The repository provides the raw force and moment measurements and the MATLAB scripts used to process the experimental data, estimate the aerodynamic control-derivative matrix (G(V)), map (G(V)) to the acceleration-derivative matrix (B(V)), construct the normalized matrix, and calculate the control-oriented metrics reported in the paper. The code was developed and tested in MATLAB. Users should consult the README file before reproducing the analysis because the scripts retain the coordinate definitions, input ordering, and normalization conventions adopted in the associated study.